U.S. patent application number 15/148434 was filed with the patent office on 2016-11-10 for externally mounted auxiliary door for an aircraft.
The applicant listed for this patent is Georgian Aerospace, LLC. Invention is credited to Michael J. Scimone.
Application Number | 20160325816 15/148434 |
Document ID | / |
Family ID | 57222298 |
Filed Date | 2016-11-10 |
United States Patent
Application |
20160325816 |
Kind Code |
A1 |
Scimone; Michael J. |
November 10, 2016 |
EXTERNALLY MOUNTED AUXILIARY DOOR FOR AN AIRCRAFT
Abstract
A door assembly for mounting on an aircraft includes a rail
mounted exteriorly to an outer skin of the aircraft, and a door
movably coupled to the rail. The door assembly also includes a
motor mountable in an interior of the aircraft, and a shaft
extending through a sealed shaft port in the outer skin of the
aircraft. The shaft couples the motor to the door, such that the
door is movable between a first position and a second position
along an outer moldline of the aircraft.
Inventors: |
Scimone; Michael J.;
(Ballwin, MO) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Georgian Aerospace, LLC |
Chesterfield |
MO |
US |
|
|
Family ID: |
57222298 |
Appl. No.: |
15/148434 |
Filed: |
May 6, 2016 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
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62158391 |
May 7, 2015 |
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Current U.S.
Class: |
1/1 |
Current CPC
Class: |
B64C 1/14 20130101; B64C
1/1407 20130101; B64C 1/1461 20130101; B64D 1/02 20130101; B64D
1/16 20130101; B64C 1/1438 20130101; B64D 47/08 20130101 |
International
Class: |
B64C 1/14 20060101
B64C001/14 |
Claims
1. A door assembly for mounting on an aircraft, the door assembly
comprising: a rail mounted exteriorly to an outer skin of the
aircraft; a door movably coupled to the rail; a motor mountable in
an interior of the aircraft; and a shaft extending through a sealed
shaft port in the outer skin of the aircraft, wherein the shaft
couples the motor to the door, such that the door is movable
between a first position and a second position along an outer
moldline of the aircraft.
2. The door assembly of claim 1, further comprising at least one
roller bearing assembly coupled to an outboard edge of the door,
the at least one roller bearing assembly received by the rail to
movably couple the door to the rail.
3. The door assembly of claim 1, further comprising a fairing
mounted on the outer skin, the fairing shaped to extend in
proximity to the outer mold line of the aircraft, the fairing
comprising: an opening adjacent a first end of the fairing; and a
cover portion adjacent a second end of the fairing opposite the
first end, the cover portion sized to receive the door in the
second position.
4. The door assembly of claim 1, wherein the shaft is a pinion
shaft, the door assembly further comprising a gear path disposed on
an interior surface of the door and configured to receive the
pinion shaft.
5. The door assembly of claim 1, wherein the door in the first
position is configured to conceal a component port defined in the
outer skin of the aircraft, and the door in the second position is
configured to reveal the component port to an exterior environment
of the aircraft.
6. The door assembly of claim 1, further comprising a manual
override mechanism operable to move the door between the first and
second positions without operation of the motor.
7. A door assembly for mounting on an aircraft, the door assembly
comprising: a rail mounted exteriorly to an outer skin of the
aircraft; a door movably coupled to the rail; an actuator system
operable to move the door between a first position and a second
position along an outer moldline of the aircraft; and a fairing
mounted on the outer skin, the fairing shaped to extend in
proximity to the outer mold line of the aircraft, the fairing
comprising: an opening adjacent a first end of the fairing; and a
cover portion adjacent a second end of the fairing opposite the
first end, the cover portion sized to receive the door in the
second position.
8. The door assembly of claim 7, further comprising at least one
roller bearing assembly coupled to an outboard edge of the door,
the at least one roller bearing assembly received by the rail to
movably couple the door to the rail.
9. The door assembly of claim 7, wherein the actuator system
comprises: a motor; and a shaft extending through a sealed shaft
port in the outer skin of the aircraft, wherein the shaft drivingly
couples the motor to the door.
10. The door assembly of claim 9, wherein the shaft is a pinion
shaft, the door assembly further comprising a gear path disposed on
an interior surface of the door and configured to receive the
pinion shaft.
11. The door assembly of claim 9, further comprising a manual
override mechanism operable to move the door between the first and
second positions without operation of the motor.
12. The door assembly of claim 7, wherein the door in the first
position is configured to conceal a component port defined in the
outer skin of the aircraft, and the door in the second position is
configured to reveal the component port to an exterior environment
of the aircraft.
13. An aircraft comprising: a component port defined in an outer
skin of the aircraft; and a door assembly comprising: a rail
mounted exteriorly to the outer skin of the aircraft; a door
movably coupled to the rail; and an actuator system operable to
move the door between a first position and a second position along
an outer moldline of the aircraft, wherein the door in the first
position conceals the component port, and the door in the second
position reveals the component port to an exterior environment of
the aircraft.
14. The aircraft of claim 13, wherein the door assembly further
comprises at least one roller bearing coupled to an outboard edge
of the door, the at least one roller bearing received by the rail
to movably couple the door to the rail.
15. The aircraft of claim 13, further comprising a fairing mounted
on the outer skin, the fairing shaped to extend in proximity to the
outer mold line of the aircraft, the fairing comprising: an opening
adjacent a first end of the fairing; and a cover portion adjacent a
second end of the fairing opposite the first end, the cover portion
sized to receive the door in the second position.
16. The aircraft of claim 13, wherein the actuator system
comprises: a motor; and a shaft extending through a sealed shaft
port in the outer skin of the aircraft, wherein the shaft drivingly
couples the motor to the door.
17. The aircraft of claim 16, wherein the shaft is a pinion shaft,
the door assembly further comprising a gear path disposed on an
interior surface of the door and configured to receive the pinion
shaft.
18. The aircraft of claim 13, further comprising a window sealingly
positioned in the component port.
19. The aircraft of claim 13, wherein the component port is
unsealed, such that at least a portion of an interior of the
aircraft is in flow communication with the exterior environment via
the component port when the door is in the second position.
20. The aircraft of claim 13, wherein the aircraft is one of a
fixed wing aircraft, a helicopter, and a lighter than air vehicle.
Description
CROSS REFERENCE TO RELATED APPLICATIONS
[0001] This application claims priority to U.S. Provisional
Application Ser. No. 62/158,391, filed May 7, 2015, the disclosure
of which is incorporated by reference in its entirety.
BACKGROUND
[0002] At least some known aircraft include payloads or other
components configured to be at least partially exposed to an
external environment while the aircraft is in flight. For example,
but not by way of limitation, the component may be an air intake, a
camera, an atmospheric monitor, another suitable sensor, ordinance,
a countermeasure, or a collection/dispersion device. At least some
such components may be positioned adjacent a port defined in the
aircraft outer skin, such as a window or open port that provides at
least partial access to the external environment. In at least some
such cases, it may be desirable to at least partially conceal the
component or the port, such as when the aircraft is not in flight
and/or the component is not in use.
[0003] This Background section is intended to introduce the reader
to various aspects of art that may be related to various aspects of
the present disclosure, which are described and/or claimed below.
This discussion is believed to be helpful in providing the reader
with background information to facilitate a better understanding of
the various aspects of the present disclosure. Accordingly, it
should be understood that these statements are to be read in this
light, and not as admissions of prior art.
BRIEF DESCRIPTION
[0004] A cover or door for mounting on an aircraft is designed to
conceal or at least partially conceal another component mounted on
the inside or outside of the aircraft, such as a port, air intake,
sight window or sight opening, a sensor, or a payload including
without limitation a camera, sensor, radome, ordinance,
countermeasure, atmospheric monitor or collection/dispersion
device. The door is suitably configured to conform or nearly
conform to the aircraft outer mold line (OML), e.g., have a
low-profile, to reduce aerodynamic drag and to minimize any effect
of the door on fuel consumption and performance of the aircraft.
The door may also be at least partially "masked" into the aircraft
OML to reduce the visibility of the door on the aircraft while
providing concealment and/or protection of components installed. As
used in this disclosure, the term "aircraft" includes without
limitation, a fixed wing airplane, rotorcraft, lighter than air
vehicle or combinations thereof, and includes piloted and remotely
controlled vehicles, as well as pylons and conformally mounted
tanks.
[0005] In one aspect, a door assembly for mounting on an aircraft
is provided. The door assembly includes a rail mounted exteriorly
to an outer skin of the aircraft, and a door movably coupled to the
rail. The door assembly also includes a motor mountable in an
interior of the aircraft, and a shaft extending through a sealed
shaft port in the outer skin of the aircraft. The shaft couples the
motor to the door, such that the door is movable between a first
position and a second position along an outer moldline of the
aircraft.
[0006] In another aspect, a door assembly for mounting on an
aircraft is provided. The door assembly includes a rail mounted
exteriorly to an outer skin of the aircraft, and a door movably
coupled to the rail. The door assembly also includes an actuator
system operable to move the door between a first position and a
second position along an outer moldline of the aircraft. The door
assembly further includes a fairing mounted on the outer skin. The
fairing is shaped to extend in proximity to the outer mold line of
the aircraft, and includes an opening adjacent a first end of the
fairing. The fairing also includes a cover portion adjacent a
second end of the fairing opposite the first end. The cover portion
is sized to receive the door in the second position.
[0007] In still another aspect, an aircraft is provided. The
aircraft includes a component port defined in an outer skin of the
aircraft, and a door assembly. The door assembly includes a rail
mounted exteriorly to the outer skin of the aircraft, and a door
movably coupled to the rail. The door assembly also includes an
actuator system operable to move the door between a first position
and a second position along an outer moldline of the aircraft. The
door in the first position conceals the component port, and the
door in the second position reveals the component port to an
exterior environment of the aircraft.
[0008] Various refinements exist of the features noted in relation
to the above-mentioned aspects. Further features may also be
incorporated in the above-mentioned aspects as well. These
refinements and additional features may exist individually or in
any combination. For instance, various features discussed below in
relation to any of the illustrated embodiments may be incorporated
into any of the above-described aspects, alone or in any
combination.
BRIEF DESCRIPTION OF THE DRAWINGS
[0009] FIG. 1 is a perspective view of an embodiment of an aircraft
including a door assembly mounted therein in accordance with this
disclosure.
[0010] FIG. 2 is a perspective view of an embodiment of the door
assembly shown in FIG. 1.
[0011] FIG. 3 is a section view of the door assembly of FIG. 1
taken along lines 3-3 shown in FIG. 2, also showing the door
mounted conformal to an aircraft moldline and structure adjacent
the door.
[0012] FIG. 4 is a perspective view of an actuator system of the
door assembly shown in FIG. 1.
[0013] FIG. 5 is another perspective external view of the aircraft
including the door assembly of FIG. 1.
[0014] FIG. 6 is a perspective view of another embodiment of an
aircraft including the door assembly of FIG. 1 mounted therein.
[0015] FIG. 7 is a side view of the aircraft and door assembly of
FIG. 6.
DETAILED DESCRIPTION
[0016] FIG. 1 is a perspective view of an embodiment of an aircraft
10 including a door assembly 100 mounted therein. FIG. 2 is a
perspective view of an example embodiment of the door assembly 100.
FIG. 3 is a section view of the door assembly 100 taken along lines
3-3 shown in FIG. 2. FIG. 3 also illustrates a door 102 of the door
assembly mounted conformal to a moldline defined by an outer skin
12 of the aircraft 10, and additional structure of the aircraft 10
adjacent the door as will be described herein. FIG. 4 is a
perspective view of an actuator system 150 of the door assembly
100.
[0017] With reference to FIGS. 1-4, the door assembly 100 includes
the door 102 and at least one rail 104 configured to be mounted
exteriorly to the aircraft outer skin 12. More specifically, the
door 102 is movably connected or coupled to each rail 104 by a door
slide mechanism 130. In the example embodiment, the at least one
rail 104 includes a pair of parallel rails 104. Each of the rails
104 extends adjacent to a respective one of a pair of opposing
outboard edges 106 of the door 102. In alternative embodiments, the
door assembly 100 includes any suitable number of rails 104 in any
suitable position with respect to the door 102. In the example
embodiment, the rails 104 are configured to be generally parallel
to a longitudinal axis X of the aircraft 10, such that the door 102
is slidable parallel to the longitudinal axis. In alternative
embodiments, the rails 104 are configured to be disposed in any
suitable direction with respect to the aircraft 10.
[0018] In the example embodiment, the actuator system 150 includes
a motor 152 housed internally within the aircraft 10, that is,
interiorly to the outer skin 12. The motor 152 is physically linked
to the door 102, and is operable to move the door 102 along the
rail 104 between a first position and a second position (shown in
FIG. 5). In the example embodiment, the motor 152 is a mechanically
driven electric motor. In alternative embodiments, the motor 152 is
any suitable motor that enables the door assembly 100 to function
as described herein.
[0019] The actuator system 150 also includes a suitable drive
system 154 coupled between the motor 152 and the door 102. The
drive system of the example embodiment has at least one gear 156
connected to a shaft or pinion 158 that extends through a shaft
port 14 in the aircraft outer skin 12 (shown in cutaway view in
FIG. 4). In the case of a pressurized aircraft the shaft port 14 is
sized to receive and to seal the shaft 158 to maintain cabin
pressure. The shaft port 14 is disposed along a plane relatively
parallel to the aircraft outer skin 12 with the shaft 158
relatively perpendicular to the skin. In alternative embodiments,
the drive system 154 operably couples the motor 152 to the door 102
in any suitable fashion.
[0020] In the example embodiment, a slot or rack gear path 160
disposed on an interior surface of the door 102 is configured to
receive the pinion shaft 158 and to enable the door to be "force"
driven by the actuator system 150. Alternatively, another suitable
interface is used, such as a belt driven system, e.g., wherein the
gear path 160 includes an intermeshing gear interface (not shown).
These types of force driven systems, wherein components of the
actuator system 150 other than the pinion shaft 158 and receiving
slot 160 are located internal to the aircraft 12, enable a
mechanical-based design with better reliability, manufacturability
and reduced risk of failure, e.g., failure of components mounted
external to the aircraft outer skin 12.
[0021] In the example embodiment, the actuator system 150 includes
a manual override mechanism 170, such as but not limited to a hand
crank, for driving the door 102 closed in case of a failure of the
primary system. A manual override switch 172 locks the manual
override mechanism 170 when not in use. In alternative embodiments,
the actuator system 150 includes any suitable manual override
system, or no manual override system.
[0022] FIG. 5 is another perspective external view of the aircraft
10 including the door assembly 100 mounted therein. With reference
to FIGS. 1-5, the door 102 moves generally linearly as it slides
along the rail 104 adjacent, and exterior to, the aircraft outer
skin 12 between a first position 120 and a second position 122. In
the example embodiment, the first position is a fully closed
position, and the second position is a fully open position. In
alternative embodiments, each of the first and second positions is
any suitable position along the rail 104. In the example
embodiment, the door 102 slides longitudinally relative to the
aircraft axis X. In alternative embodiments, the door 102 slides
along the rail 104 disposed in any suitable direction relative to
the aircraft 10, such as laterally.
[0023] In certain embodiments, the door slide mechanism 130
coupling the door 102 to the at least one rail 104 is designed to
prevent or eliminate the possibility of door "racking" or sticking,
e.g., where the door 102 does not fully extend to the first
position 120 or fully retract to the second position 122. As a
non-limiting example, as shown in FIG. 3, the door slide mechanism
130 includes at least one roller bearing assembly 132 positioned
along the outboard edge 106 of the door. Each roller bearing
assembly includes a roller bearing 134 loaded by a spring 136 to
prevent racking of the door 102 during translation along the rail
104 by the drive system 154. In alternative embodiments, the door
slide mechanism 130 reduces or eliminates the possibility of door
"racking" or sticking in any other suitable fashion.
[0024] In the example embodiment, as shown in FIG. 2, the door
slide mechanism 130 includes three roller bearing assemblies 132
spaced apart along each outboard edge 106 of the door 102. In
alternative embodiments, the door slide mechanism 130 includes any
suitable number of roller bearing assemblies 132 spaced in any
suitable fashion along each outboard edge 106. In addition, the
door slide mechanism 130 may include guide pins (not shown) located
intermediately along each outboard edge 106 to ensure a smooth
transition. In certain embodiments, the door slide mechanism 130
defines a space 138 (shown in FIG. 3) between the outboard edge 104
and the rail 104 sufficient to enable movement of the door 102
regardless of bending of the door and surrounding structure, e.g.,
due to expansion/contraction or bending during flight.
[0025] Each rail 104 of this embodiment is mounted on the aircraft
10 using a suitable mounting structure 108. In the illustrated
embodiment, the mounting structure 108 includes a bracket of
L-shaped cross-section extending adjacent the rail 104, with one
"leg" of the L coupled to the aircraft outer skin 12 and the other
"leg" of the L coupled to the rail 104. In alternative embodiments,
each rail 104 is coupled to the aircraft in any suitable fashion
that enables the door assembly 100 to function as described
herein.
[0026] As illustrated in FIG. 3, a component port 18 is defined in,
and extends through, the aircraft outer skin 12 proximate the door
assembly 100. Moreover, in some such embodiments, a component 20 is
positioned internally within the aircraft 10, interiorly and
adjacent to the component port 18. More specifically, the component
port 18 and the component 20 are positioned with respect to the
door assembly 100 such that the door 102 in the first position
hides or conceals the component port 18 and the component 20 from
external view, and the door 102 in the second position reveals the
component port 18, thereby enabling access by the component 20 to
an exterior environment of the aircraft 10 via the component port
18.
[0027] In the illustrated embodiment, a window 22 is sealingly
positioned in the component port 18, such that cabin pressure is
maintained interiorly to the outer skin 12 proximate the component
20. For example, the component 20 is an electromagnetic sensor
system or human observer, and the window 22 is transparent to at
least one electromagnetic wavelength detectable by the sensor
system 20 or the human observer, while enabling the aircraft 10 to
maintain cabin pressure. In alternative embodiments, the component
port 18 is unsealed, i.e. open, such that at least a portion of the
interior of the aircraft 10 is in flow communication with the
environment exterior to the outer skin 12 via the component port 18
when the door 102 is in the second position 122. For example, the
component 20 is a collection/dispersion device, and the component
port 18 enables flow communication between the component 20 and the
atmosphere external to the aircraft 10. In some such embodiments,
the interior of the aircraft 10 proximate the component 20 is
sealed off in a suitable fashion from a pressurized portion of the
aircraft cabin. In particular, the sealed shaft port 14, as
described above, enables the actuator system 150 to be accessible
to crew in the pressurized portion of the aircraft cabin adjacent
the unsealed component port 18.
[0028] When the door 102 is in the open position and the component
port 18 is not sealed, a sensor (not shown) may be extended through
the component port 18 from the component 20. For example, the
sensor may include a camera/sensor/radome that is mounted on an
elevator to extend the unit during use and retract to a stored
position when not in use. The cloaking door 102 in the closed
position would conceal and protect the sensor.
[0029] As discussed above, the component port 18 of the unsealed
variety may be configured for atmospheric data collection, the
dispensing of ordnance, countermeasures, or dispersing materials
into the atmosphere, such as liquid, aerosol or dry materials
including fire retardant, silver iodide, and/or environmentally
friendly defoliant, as examples without limitation.
[0030] The door assembly 100 in this example embodiment protects
and/or conceals component 20. The component may be an
extendable/deployable sensor or other payload. The payload or
sensor may be extendable or deployable throughout the aircraft
flight envelope, or only in a portion of the flight envelope. The
door 102 may be controlled or moved to the second or open position
122 by a suitable control system (not shown) when required by the
mission or payload operation. Thereafter, the door 102 can be
controlled to move to its first or closed position 120. In this
closed position, the payload is concealed, and the door 102 itself
is difficult to see or visualize.
[0031] The door operation may be controlled by a flight crew or,
alternatively, remote operator controlled. Control may be based on
factors including the equipment installed and mission requirements.
Control may also be automatic in some cases, such as automatic
closure when the landing gear are extended for landing. The
controlling function can be mechanized by different means
electrically or mechanically. As discussed above, the door actuator
system 150 may also include a mechanical backup such as the manual
override mechanism 170 in case of electrical motor failure. For
example, the mechanical backup can be mechanized to allow for
emergency extension or retraction by the crew via the cranking
handle (shown in FIG. 4) or a pump.
[0032] In another embodiment, the component port 18 is again of the
unsealed variety, and serves as an auxiliary air intake that is
used to allow air to enter into the aircraft and/or engine through
a port. Several different types of inlet ports may be used in
combination with the door assembly 100. OML or near OML inlet ports
can include an open inlet duct, open inlet plenum, an inlet screen,
a particle separator or a barrier filter. As examples, the
component port 18 may include a pair of adjacent component ports 18
of different inlet types, and the door 102 may be selectively
controlled between the first and second positions to change between
the inlet types, or may be open or closed to protect an inlet port.
The component port 18 may provide an air intake for environmental
air, engine intake, or Auxiliary Power Unit (APU) intake among
other examples.
[0033] FIG. 6 is a perspective view of another embodiment of the
aircraft 10 including the door assembly 100 mounted therein. FIG. 7
is a side view of the aircraft 10 and door assembly 100 shown in
FIG. 6. With reference to FIGS. 2-4, 6, and 7, in the illustrated
embodiment, the door assembly 100 includes a fairing 110 mounted on
the aircraft outer skin 12. The fairing 110 is shaped to extend in
proximity to the OML of the aircraft 10. The fairing defines an
opening 114 adjacent a first end of the fairing. The opening 114 is
at least partially aligned with the component port 18, such that
the fairing 110 does not obstruct the component port 18 when the
door 102 is in the second position 122. The fairing 110 also
includes a cover portion 112 adjacent a second end of the fairing
opposite the first end. The cover portion 112 is sized to receive
the door 102 in the second or open position 122. In some
embodiments, the fairing 110 reduces a dynamic pressure that tends
to resist movement of the door 102 between the first and second
positions when the aircraft 10 is in flight, thereby improving a
controllability of the door 102 and/or decreasing a power required
from the motor 152.
[0034] In this embodiment, the rails 104 are mounted to the fairing
110. In other embodiments, the rail or rails 104 is mounted
directly to the outer skin 12, for example in the same fashion as
discussed above with respect to the mounting structure 108.
[0035] The door assembly 100 mounted on an aircraft as disclosed
herein will accommodate operation of the aircraft in forward flight
up to the limits of the aircraft ground and flight envelope, or
through the ground or flight envelope of a rotorcraft including
hover conditions, and in the case of a lighter than air vehicle
throughout the flight envelope.
[0036] When introducing elements of the present invention or the
embodiment(s) thereof, the articles "a", "an", "the" and "said" are
intended to mean that there are one or more of the elements. The
terms "comprising", "including" and "having" are intended to be
inclusive and mean that there may be additional elements other than
the listed elements.
[0037] As various changes could be made in the above constructions
and methods without departing from the scope of the invention, it
is intended that all matter contained in the above description and
shown in the accompanying drawings shall be interpreted as
illustrative and not in a limiting sense.
* * * * *